11096 Federal Register / Vol. 80, No. 40 / Monday, March 2, 2015 / Rules and Regulations 

(3) Continuing education/training 

standards for State directors of school 

nutrition programs and distributing 

agencies. Each school year, all State 

directors with responsibility for the 

National School Lunch Program under 

part 210 of this chapter and the School 

Breakfast Program under part 220 of this 

chapter, as well as those responsible for 

the distribution of USDA donated foods 

under part 250 of this chapter, must 

complete a minimum of 15 hours of 

training in core areas that may include 

nutrition, operations, administration, 

communications and marketing. 

Additional hours and topics may be 

specified by FNS, as needed, to address 

Program integrity and other critical 

issues. 

(4) Provision of annual training. At 

least annually, State agencies with 

responsibility for the National School 

Lunch Program under part 210 of this 

chapter and the School Breakfast 

Program under part 220 of this chapter, 

as well as State agencies with 

responsibility for the distribution of 

USDA donated foods under part 250 of 

this chapter, must provide or ensure 

that State agency staff receive annual 

continuing education/training. (i) Each State agency with 

responsibility for the National School 

Lunch Program under part 210 of this 

chapter and the School Breakfast 

Program under part 220 of this chapter 

must provide a minimum of 18 hours of 

continuing education/training to school 

food authorities. Topics include 

administrative practices (including 

training in application, certification, 

verification, meal counting, and meal 

claiming procedures); the accuracy of 

approvals for free and reduced price 

meals; the identification of reimbursable 

meals at the point of service; nutrition; 

health and food safety standards; the 

efficient and effective use of USDA 

donated foods; and any other 

appropriate topics, as determined by 

FNS, to ensure program compliance and 

integrity or to address other critical 

issues. 

(ii) Each State agency with 

responsibility for the distribution of 

USDA donated foods under part 250 of 

this chapter must provide or ensure 

receipt of continuing education/training 

to State distribution agency staff on an 

annual basis. Topics may include the 

efficient and effective use of USDA 

donated foods; inventory rotation and 

control; health and food safety 

standards; and any other appropriate 

topics, as determined by FNS, to ensure 

program compliance and integrity or to 

address other critical issues. 

(5) Records and recordkeeping. State 

agencies must annually retain records 

for a period of three years to adequately 

demonstrate compliance with the 

professional standards for State 

directors of school nutrition programs 

established in this paragraph. 

(6) Failure to comply. Failure to 

comply with the professional standards 

in this paragraph may result in 

sanctions as specified in paragraph (b) 

of this section. 

■ 13. Revise § 235.12 to read as follows: 

§ 235.12 Information collection/

recordkeeping—OMB assigned control 

numbers. 

7 CFR Section 

where 

requirements 

are 

described 

Current OMB control No. 

235.3(b) .......... 0584–0067. 

235.4 ............... 0584–0067. 

235.5(b), (d) .... 0584–0067. 

235.7(a), (b) .... 0584–0067. 

235.9(c), (d) .... 0584–0067. 

235.11 ............. 0584–0067. 

210.7 ............... 0584–0067. 

Dated: February 24, 2015. 

Audrey Rowe, 

Administrator, Food and Nutrition Service. 

[FR Doc. 2015–04234 Filed 2–27–15; 8:45 am] 

BILLING CODE 3410–30–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0139; Directorate 

Identifier 2012–NM–133–AD; Amendment 

39–18081; AD 2015–02–14] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are superseding 

Airworthiness Directive (AD) 2009–20– 

05 for certain Airbus Model A318, 

A319, A320, and A321 series airplanes. 

AD 2009–20–05 required one-time 

inspections for cracking, damage, 

correct installation, and correct 

adjustment of the main landing gear 

(MLG) door hinge and actuator fittings 

on the keel beam, and corrective actions 

if necessary. This new AD expands the 

applicability, reduces the compliance 

time, and requires repetitive inspections 

instead of the one-time inspection. This 

AD also requires revising the 

maintenance or inspection program. 

This AD was prompted by reports of 

cracks on fittings that had successfully 

passed certain required inspections. We 

are issuing this AD to detect and correct 

cracking on the MLG door hinge fitting 

and actuator fitting on the keel beam, 

which could lead to in-flight 

detachment of an MLG door, possibly 

resulting in injury to persons on the 

ground and/or damage to the airplane. 

DATES: This AD becomes effective April 

6, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of April 6, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain other publications listed in 

this AD as of November 3, 2009 (74 FR 

49795, September 29, 2009). 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2014-0139; or in 

person at the Docket Management 

Facility, U.S. Department of 

Transportation, Docket Operations, 

M–30, West Building Ground Floor, 

Room W12–140, 1200 New Jersey 

Avenue SE., Washington, DC. 

For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EIAS, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 

61 93 44 51; email account.airwortheas@airbus.com; Internet http://

www.airbus.com. You may view this 

referenced service information at the 

FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. 

For information on the availability of 

this material at the FAA, call 425–227– 

1221. It is also available on the Internet 

at http://www.regulations.gov by 

searching for and locating Docket No. 

FAA–2014–0139. 

FOR FURTHER INFORMATION CONTACT: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, 

Transport Airplane Directorate, FAA, 

1601 Lind Avenue SW., Renton, WA 

98057–3356; telephone 425–227–1405; 

fax 425–227–1149. 

SUPPLEMENTARY INFORMATION: 

Discussion 

We issued a notice of proposed 

rulemaking (NPRM) to amend 14 CFR 

part 39 to supersede AD 2009–20–05, 

Amendment 39–16028 (74 FR 49795, 

September 29, 2009). AD 2009–20–05 

applied to certain Model A318, A319, 

A320, and A321 series airplanes. The 

NPRM published in the Federal 

Register on March 12, 2014 (79 FR 

13925). 


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Federal Register / Vol. 80, No. 40 / Monday, March 2, 2015 / Rules and Regulations 11097 

The European Aviation Safety Agency 

(EASA), which is the Technical Agent 

for the Member States of the European 

Union, has issued EASA Airworthiness 

Directive 2012–0118, dated July 4, 2012 

(referred to after this as the Mandatory 

Continuing Airworthiness Information, 

or ‘‘the MCAI’’), to correct an unsafe 

condition on the specified products. 

The MCAI states: 

Several cases of cracks have reportedly 

been found on the MLG door hinge fitting 

and on the MLG door actuator fitting on the 

keel beam. 

This condition, if not detected and 

corrected, could lead to in-flight detachment 

of a MLG door, possibly resulting in injury 

to persons on the ground and/or damage to 

the aeroplane. 

To address this potential unsafe condition, 

EASA issued EASA AD 2007–0161 [http://

ad.easa.europa.eu/blob/easa_ad_2007_0161_

superseded.pdf/AD_2007-0161_1] [which 

corresponds to FAA AD 2009–20–05, 

Amendment 39–16028 (74 FR 49795, 

September 29, 2009)], to require a one-time 

inspection of the affected fittings and 

accomplishment of the applicable corrective 

actions. 

Since that [EASA] AD was issued, some 

cracks have been found on fittings that had 

successfully passed the one-time inspection 

as required by EASA AD 2007–0161. 

Analyses of these cracks have lead Airbus to 

reconsider the repetitive inspections of the 

MLG door hinge and actuator fittings on the 

keel beam, in accordance with the ALI task 

533154–02–1 requirement as defined in 

Airbus A318/A319/A320/A321 

Airworthiness Limitation Items (ALI) 

Document, by introducing more restrictive 

inspection thresholds and intervals. 

For the reasons stated above, this [EASA] 

AD, which supersedes EASA AD 2007–0161 

and the ALI [Airworthiness Limitations Item] 

task 533154–02–1 requirements, expands the 

[EASA] AD applicability to all A318/A319/

A320/A321 aeroplanes and requires 

repetitive inspections of the MLG door hinge 

and actuator fittings on the keel beam at a 

new threshold and interval and, depending 

on findings, the accomplishment of 

applicable corrective actions. 

The inspections are detailed, high 

frequency eddy current (HFEC), and 

ultrasonic inspections for cracking, 

damage, correct installation, and correct 

adjustment, as applicable. The 

corrective actions include correcting 

incorrect adjustments and installations, 

and repair. This AD also requires 

revising the maintenance or inspection 

program, as applicable, to remove ALI 

task 533154–02–1. You may examine 

the MCAI in the AD docket on the 

Internet at http://www.regulations.gov/

#!documentDetail;D=FAA-2014-0139- 

0002. 

Comments 

We gave the public the opportunity to 

participate in developing this AD. The 

following presents the comments 

received on the NPRM (79 FR 13925, 

March 12, 2014) and the FAA’s response 

to each comment. 

Requests To Reference Revised Service 

Bulletins 

Airbus and United Airlines (UAL) 

requested that we reference Airbus 

Service Bulletin A320–53–1195, 

Revision 05, dated November 22, 2013; 

and Airbus Service Bulletin A320–53– 

1196, Revision 04, dated November 22, 

2013; as appropriate sources of service 

information. 

We agree with the commenters’ 

requests to reference Airbus Service 

Bulletin A320–53–1195, Revision 05, 

dated November 22, 2013; and Airbus 

Service Bulletin A320–53–1196, 

Revision 04, dated November 22, 2013; 

as appropriate sources of service 

information for accomplishing the 

required actions in this AD. No 

additional work is specified by these 

service bulletin revisions for airplanes 

modified by any previous issue. We 

added a new paragraph (l) to this AD 

and redesignated subsequent paragraphs 

accordingly. New paragraph (l) gives 

credit for actions accomplished using 

certain service information before the 

effective date of this AD. 

We have revised paragraph (i)(1) of 

this AD to refer to Airbus Service 

Bulletin A320–53–1195, Revision 05, 

dated November 22, 2013, and added 

paragraph (l)(1) to this AD to give credit 

for actions accomplished previously 

using Airbus Service Bulletin A320–53– 

1195, Revision 03, dated November 8, 

2011; or Airbus Service Bulletin A320– 

53–1195, Revision 04, dated August 22, 

2012. 

We have revised paragraph (i)(2) of 

this AD to refer to Airbus Service 

Bulletin A320–53–1196, Revision 04, 

dated November 22, 2013; and added 

paragraph (l)(2) to this AD to give credit 

for actions accomplished using Airbus 

Service Bulletin A320–53–1196, 

Revision 02, dated November 8, 2011; or 

Airbus Service Bulletin A320–53–1196, 

Revision 03, dated August 22, 2012. 

Request To Refer to Additional Service 

Information for Task Removal 

UAL requested that we revise 

paragraph (k) of the proposed AD (79 FR 

13925, March 12, 2014) to reference 

Airbus A318/A319/A320/A321 

Airworthiness Limitation Items, 

Document AI/S–M4/95A.0252/96, Issue 

10, dated October 2009; or Issue 11, 

dated September 2010; in addition to 

Airbus A318/A319/A320/A321 ALS 

Part 2—Damage Tolerant Airworthiness 

Limitations Items (DT ALI), Revision 01, 

dated April 4, 2012. UAL stated that 

Task 533154–02–1 of the Airbus A318/ 

A319/A320/A321 ALS Part 2—Damage 

Tolerant Airworthiness Limitations 

Items (DT ALI), Revision 01, dated April 

4, 2012, is ‘‘superseded by Airbus 

Service Bulletins A320–53–1195 and 

A320–53–1196.’’ UAL explained that 

operators that comply with Airbus 

A318/A319/A320/A321 ALS Part 2— 

Damage Tolerant Airworthiness 

Limitations Items (DT ALI), Revision 01, 

dated April 4, 2012, should already 

have removed Task 533154–02–1 from 

their maintenance/inspection programs. 

UAL also explained that operators might 

not have Airbus A318/A319/A320/A321 

ALS Part 2—Damage Tolerant 

Airworthiness Limitations Items (DT 

ALI), Revision 01, dated April 4, 2012, 

in their maintenance/inspection 

programs and instead might have Airbus 

A318/A319/A320/A321 Airworthiness 

Limitation Items, Document AI/SE–M4/ 

95A.0252/96, Issue 10, dated October 

2009; or Issue 11, dated September 

2010. 

We agree with the commenter’s 

request to refer to Airbus A318/A319/

A320/A321 Airworthiness Limitation 

Items, Document AI/SE–M4/95A.0252/

96, Issue 10, dated October 2009; or 

Issue 11, dated September 2010; in 

paragraph (k) of this AD. This revision 

will ensure that the actions specified by 

Task 533154–02–1 are removed from an 

operator’s maintenance inspection 

program. 

Request To Remove Reporting 

Requirement 

UAL requested that we not require 

reporting, as described in the service 

information, if no damage and/or cracks 

are found during the inspection of the 

hinge fittings. UAL stated that reporting 

has insignificant value and is a burden 

on the operator. UAL explained that, 

since the inspections must be 

repetitively accomplished, the rate of 

reporting no findings will be significant 

without adding valued information, and 

that any damage/cracks will be reported 

to Airbus when they are contacted for 

repair approval. 

We disagree with the commenter’s 

request to remove the reporting action 

required by this AD. A reporting 

requirement is instrumental in ensuring 

that we can gather as much information 

as possible regarding the extent and 

nature of the identified unsafe 

condition, especially in cases where that 

data may not be available through other 

established means. Also, the commenter 

did not provided any rationale 

concerning how eliminating the 

reporting requirement will ensure that 

future service information from Airbus 

will continue to maintain operational 


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11098 Federal Register / Vol. 80, No. 40 / Monday, March 2, 2015 / Rules and Regulations 

safety of the fleet. We have not changed 

this AD in this regard. 

Request To Remove Requirement To 

Refer to This AD in Repair Approvals 

UAL requested that we remove the 

statement ‘‘for a repair method to be 

approved, the repair approval must 

specifically refer to this AD’’ in 

paragraph (i) of the proposed AD (79 FR 

13925, March 12, 2014). UAL stated that 

this statement could have a significant 

impact on the financial cost and 

customer support between the operator 

and Airbus. UAL also stated that this 

statement should be removed for those 

general reasons stated in A4A’s 

comment on the same topic in NPRM 

2012–NM–101–AD (78 FR 78285, 

December 26, 2013), which stated, 

among other justifications, that ‘‘The 

added costs for this AD and all that may 

follow bearing the new procedural 

wording represent an unfair burden 

placed solely on U.S. registered 

aircraft.’’ 

We concur with the commenter’s 

request to remove the requirement to 

include the AD reference in repair 

approvals. Since late 2006, we have 

included a standard paragraph titled 

‘‘Airworthy Product’’ in all MCAI ADs 

in which the FAA develops an AD 

based on a foreign authority’s AD. The 

MCAI or referenced service information 

in an FAA AD often directs the owner/ 

operator to contact the manufacturer for 

corrective actions, such as a repair. 

Briefly, the Airworthy Product 

paragraph allowed owners/operators to 

use corrective actions provided by the 

manufacturer if those actions were FAAapproved. In addition, the paragraph 

stated that any actions approved by the 

State of Design Authority (or its 

delegated agent) are considered to be 

FAA-approved. 

In the NPRM (79 FR 13925, March 12, 

2014), we proposed to prevent the use 

of repairs that were not specifically 

developed to correct the unsafe 

condition, by requiring that the repair 

approval provided by the State of 

Design Authority or its delegated agent 

specifically refer to this FAA AD. This 

change was intended to clarify the 

method of compliance and to provide 

operators with better visibility of repairs 

that are specifically developed and 

approved to correct the unsafe 

condition. In addition, we proposed to 

change the phrase ‘‘its delegated agent’’ 

to include ‘‘the Design Approval Holder 

(DAH) with a State of Design 

Authority’s design organization 

approval (DOA)’’ to refer to a DAH 

authorized to approve required repairs 

for the AD. 

Comments were provided to the 

NPRM (79 FR 13925, March 12, 2014) 

and to an NPRM referenced by the 

commenter (i.e., Directorate Identifier 

2012–NM–101–AD (78 FR 78285, 

December 26, 2013)) about these 

proposed changes. One commenter to 

the NPRM having Directorate Identifier 

2012–NM–101–AD, United Parcel 

Service (UPS), stated the following: 

‘‘The proposed wording, being specific 

to repairs, eliminates the interpretation 

that Airbus messages are acceptable for 

approving minor deviations (corrective 

actions) needed during accomplishment 

of an AD mandated Airbus service 

bulletin.’’ 

This comment has made the FAA 

aware that some operators have 

misunderstood or misinterpreted the 

Airworthy Product paragraph to allow 

the owner/operator to use messages 

provided by the manufacturer as 

approval of deviations during the 

accomplishment of an AD-mandated 

action. The Airworthy Product 

paragraph does not approve messages or 

other information provided by the 

manufacturer for deviations to the 

requirements of the AD-mandated 

actions. The Airworthy Product 

paragraph only addresses the 

requirement to contact the manufacturer 

for corrective actions for the identified 

unsafe condition and does not cover 

deviations from other AD requirements. 

However, deviations to AD-required 

actions are addressed in 14 CFR 39.17, 

and anyone may request the approval 

for an alternative method of compliance 

to the AD-required actions using the 

procedures found in 14 CFR 39.19. 

To address this misunderstanding and 

misinterpretation of the Airworthy 

Product paragraph, we have changed 

that paragraph and retitled it 

‘‘Contacting the Manufacturer.’’ This 

paragraph now clarifies that for any 

requirement in this AD to obtain 

corrective actions from a manufacturer, 

the actions must be accomplished using 

a method approved by the FAA, EASA, 

or Airbus’s EASA DOA. 

The Contacting the Manufacturer 

paragraph also clarifies that, if approved 

by the DOA, the approval must include 

the DOA-authorized signature. The DOA 

signature indicates that the data and 

information contained in the document 

are EASA-approved, which is also FAAapproved. Messages and other 

information provided by the 

manufacturer that do not contain the 

DOA-authorized signature approval are 

not EASA-approved, unless EASA 

directly approves the manufacturer’s 

message or other information. 

This clarification does not remove 

flexibility afforded previously by the 

Airworthy Product paragraph. 

Consistent with long-standing FAA 

policy, such flexibility was never 

intended for required actions. This is 

also consistent with the 

recommendation of the AD 

Implementation Aviation Rulemaking 

Committee to increase flexibility in 

complying with ADs by identifying 

those actions in manufacturers’ service 

instructions that are ‘‘Required for 

Compliance’’ with ADs. We continue to 

work with manufacturers to implement 

this recommendation. But once we 

determine that an action is required, any 

deviation from the requirement must be 

approved as an alternative method of 

compliance. 

Other commenters to NPRM 2012– 

NM–101–AD (78 FR 78285, December 

26, 2013) pointed out that in many cases 

the foreign manufacturer’s service 

bulletin and the foreign authority’s 

MCAI may have been issued some time 

before the FAA AD. Therefore, the DOA 

may have provided U.S. operators with 

an approved repair, developed with full 

awareness of the unsafe condition, 

before the FAA AD is issued. Under 

these circumstances, to comply with the 

FAA AD, the operator would be 

required to go back to the 

manufacturer’s DOA and obtain a new 

approval document, adding time and 

expense to the compliance process with 

no safety benefit. 

Based on these comments, we 

removed the requirement from this AD 

that the DAH-provided repair 

specifically refer to this AD. Before 

adopting such a requirement in the 

future, the FAA will coordinate with 

affected DAHs and verify they are 

prepared to implement means to ensure 

that their repair approvals consider the 

unsafe condition addressed in an AD. 

Any such requirements will be adopted 

through the normal AD rulemaking 

process, including notice-and-comment 

procedures, when appropriate. 

We have also decided not to include 

a generic reference to either the 

‘‘delegated agent’’ or the ‘‘DAH with 

State of Design Authority design 

organization approval,’’ but instead we 

will provide the specific delegation 

approval granted by the State of Design 

Authority for the DAH. 

Conclusion 

We reviewed the available data, 

including the comments received, and 

determined that air safety and the 

public interest require adopting this AD 

with the changes described previously 

and minor editorial changes. We have 

determined that these changes: 

• Are consistent with the intent that 

was proposed in the NPRM (79 FR 


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Federal Register / Vol. 80, No. 40 / Monday, March 2, 2015 / Rules and Regulations 11099 

13925, March 12, 2014) for correcting 

the unsafe condition; and 

• Do not add any additional burden 

upon the public than was already 

proposed in the NPRM (79 FR 13925, 

March 12, 2014). 

We also determined that these 

changes will not increase the economic 

burden on any operator or increase the 

scope of this AD. 

Related Service Information Under 1 

CFR Part 51 

We reviewed Airbus Service Bulletin 

A320–53–1195, Revision 05, dated 

November 22, 2013, which describes 

procedures for inspections of the MLG 

door actuator fittings on the keel beam, 

and corrective actions if necessary. We 

also reviewed Airbus Service Bulletin 

A320–53–1196, Revision 04, dated 

November 22, 2013, which describes 

procedures for inspections of the MLG 

door hinge fitting on the keel beam, and 

corrective actions if necessary. This 

service information is reasonably 

available; see ADDRESSES for ways to 

access this service information. 

Costs of Compliance 

We estimate that this AD affects 851 

airplanes of U.S. registry. 

The actions that are required by AD 

2009–20–05, Amendment 39–16028 (74 

FR 49795, September 29, 2009), and 

retained in this AD take about 28 workhours per product, at an average labor 

rate of $85 per work-hour. Based on 

these figures, the estimated cost of the 

actions that were required by AD 2009– 

20–05 is $2,380 per product. 

We also estimate that it will take 

about 26 work-hours per product to 

comply with the basic requirements of 

this AD. The average labor rate is $85 

per work-hour. Based on these figures, 

we estimate the cost of this AD on U.S. 

operators to be $1,880,710, or $2,210 per 

product. 

We have received no definitive data 

that would enable us to provide cost 

estimates for the on-condition actions 

specified in this AD. 

Paperwork Reduction Act 

A federal agency may not conduct or 

sponsor, and a person is not required to 

respond to, nor shall a person be subject 

to penalty for failure to comply with a 

collection of information subject to the 

requirements of the Paperwork 

Reduction Act unless that collection of 

information displays a current valid 

OMB control number. The control 

number for the collection of information 

required by this AD is 2120–0056. The 

paperwork cost associated with this AD 

has been detailed in the Costs of 

Compliance section of this document 

and includes time for reviewing 

instructions, as well as completing and 

reviewing the collection of information. 

Therefore, all reporting associated with 

this AD is mandatory. Comments 

concerning the accuracy of this burden 

and suggestions for reducing the burden 

should be directed to the FAA at 800 

Independence Ave. SW., Washington, 

DC 20591, ATTN: Information 

Collection Clearance Officer, AES–200. 

Authority for This Rulemaking 

Title 49 of the United States Code 

specifies the FAA’s authority to issue 

rules on aviation safety. Subtitle I, 

section 106, describes the authority of 

the FAA Administrator. ‘‘Subtitle VII: 

Aviation Programs,’’ describes in more 

detail the scope of the Agency’s 

authority. 

We are issuing this rulemaking under 

the authority described in ‘‘Subtitle VII, 

Part A, Subpart III, Section 44701: 

General requirements.’’ Under that 

section, Congress charges the FAA with 

promoting safe flight of civil aircraft in 

air commerce by prescribing regulations 

for practices, methods, and procedures 

the Administrator finds necessary for 

safety in air commerce. This regulation 

is within the scope of that authority 

because it addresses an unsafe condition 

that is likely to exist or develop on 

products identified in this rulemaking 

action. 

Regulatory Findings 

We determined that this AD will not 

have federalism implications under 

Executive Order 13132. This AD will 

not have a substantial direct effect on 

the States, on the relationship between 

the national government and the States, 

or on the distribution of power and 

responsibilities among the various 

levels of government. 

For the reasons discussed above, I 

certify that this AD: 

1. Is not a ‘‘significant regulatory 

action’’ under Executive Order 12866; 

2. Is not a ‘‘significant rule’’ under the 

DOT Regulatory Policies and Procedures 

(44 FR 11034, February 26, 1979); 

3. Will not affect intrastate aviation in 

Alaska; and 

4. Will not have a significant 

economic impact, positive or negative, 

on a substantial number of small entities 

under the criteria of the Regulatory 

Flexibility Act. 

Examining the AD Docket 

You may examine the AD docket on 

the Internet at http:// 

www.regulations.gov/ 

#!docketDetail;D=FAA-2014-0139; or in 

person at the Docket Management 

Facility between 9 a.m. and 5 p.m., 

Monday through Friday, except Federal 

holidays. The AD docket contains this 

AD, the regulatory evaluation, any 

comments received, and other 

information. The street address for the 

Docket Operations office (telephone 

800–647–5527) is in the ADDRESSES

section. 

List of Subjects in 14 CFR Part 39 

Air transportation, Aircraft, Aviation 

safety, Incorporation by reference, 

Safety. 

Adoption of the Amendment 

Accordingly, under the authority 

delegated to me by the Administrator, 

the FAA amends 14 CFR part 39 as 

follows: 

PART 39—AIRWORTHINESS 

DIRECTIVES 

■ 1. The authority citation for part 39 

continues to read as follows: 

Authority: 49 U.S.C. 106(g), 40113, 44701. 

§ 39.13 [Amended] 

■ 2. The FAA amends § 39.13 by 

removing Airworthiness Directive (AD) 

2009–20–05, Amendment 39–16028 (74 

FR 49795, September 29, 2009), and 

adding the following new AD: 

2015–02–14 Airbus: Amendment 39–18081. 

Docket No. FAA–2014–0139; Directorate 

Identifier 2012–NM–133–AD. 

(a) Effective Date 

This AD becomes effective April 6, 2015. 

(b) Affected ADs 

This AD replaces AD 2009–20–05, 

Amendment 39–16028 (74 FR 49795, 

September 29, 2009). 

(c) Applicability 

This AD applies to the Airbus airplanes 

specified in paragraphs (c)(1), (c)(2), (c)(3), 

and (c)(4) of this AD, certificated in any 

category, all manufacturer serial numbers 

(MSNs). 

(1) Model A318–111, –112, –121, and –122 

airplanes. 

(2) Model A319–111, –112, –113, –114, 

–115, –131, –132, and –133 airplanes. 

(3) Model A320–211, –212, –214, –231, 

–232, and –233 airplanes. 

(4) Model A321–111, –112, –131, –211, 

–212, –213, –231, and –232 airplanes. 

(d) Subject 

Air Transport Association (ATA) of 

America Code 53, Fuselage. 

(e) Reason 

This AD was prompted by reports of cracks 

on the main landing gear (MLG) door hinge 

fitting and actuator fitting on the keel beam. 

We are issuing this AD to detect and correct 

cracking on the MLG door hinge fitting and 

actuator fitting on the keel beam, which 

could lead to in-flight detachment of an MLG 

door, possibly resulting in injury to persons 

on the ground and/or damage to the airplane. 


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11100 Federal Register / Vol. 80, No. 40 / Monday, March 2, 2015 / Rules and Regulations 

(f) Compliance 

Comply with this AD within the 

compliance times specified, unless already 

done. 

(g) Retained One-Time Inspections and 

Corrective Action 

This paragraph restates the requirements of 

paragraphs (f)(1) and (f)(2) of AD 2009–20– 

05, Amendment 39–16028 (74 FR 49795, 

September 29, 2009), with specific delegation 

approval language. For airplanes having 

serial numbers up to MSN 2850 inclusive, 

except MSNs 0115, 0184, 0782, 1151, 1190, 

2650, 2675, 2706, 2801, and 2837: Do the 

actions required by paragraphs (g)(1) and 

(g)(2) of this AD. 

(1) At the latest of the times specified in 

paragraphs (g)(1)(i), (g)(1)(ii), and (g)(1)(iii) of 

this AD: Perform detailed visual, high 

frequency eddy current (HFEC), and 

ultrasonic inspections (for cracking, damage, 

correct installation, and correct adjustment, 

as applicable) of the left-hand (LH) and righthand (RH) MLG door actuator fitting on the 

keel beam, and do all applicable corrective 

actions before further flight, except as 

provided by paragraph (h) of this AD. Do all 

actions required by this paragraph in 

accordance with the Accomplishment 

Instructions of Airbus Mandatory Service 

Bulletin A320–53–1195, Revision 02, 

including Appendix 01, dated April 5, 2007; 

except where that service information 

specifies that the applicable corrective action 

is contacting Airbus, contact Airbus for 

repair instructions and repair before further 

flight. As of the effective date of this AD, 

where that service information specifies that 

the applicable corrective action is contacting 

Airbus, before further flight, repair using a 

method approved by the Manager, ANM–116, 

Transport Airplane Directorate, FAA; or the 

European Aviation Safety Agency (EASA); or 

Airbus’s EASA Design Organization 

Approval (DOA). 

(i) Within 6,000 flight cycles since first 

flight. 

(ii) Within 1,500 flight cycles after 

November 3, 2009 (the effective date of AD 

2009–20–05, Amendment 39–16028 (74 FR 

49795, September 29, 2009)). 

(iii) Within 6,000 flight cycles from the 

latest MLG door actuator fitting replacement. 

(2) At the later of the times specified in 

paragraphs (g)(2)(i) and (g)(2)(ii) of this AD: 

Perform detailed visual and HFEC 

inspections (for cracking, damage, correct 

installation, and correct adjustment, as 

applicable) of the LH and RH MLG door 

hinge fitting on the keel beam, and do all 

applicable corrective actions before further 

flight, except as provided by paragraph (h) of 

this AD. Do all actions required by this 

paragraph in accordance with the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A320–53–1196, 

Revision 01, including Appendix 01, dated 

November 29, 2006; except where that 

service information specifies that the 

applicable corrective action is contacting 

Airbus, contact Airbus for repair instructions 

and repair before further flight. As of the 

effective date of this AD, where that service 

information specifies that the applicable 

corrective action is contacting Airbus, before 

further flight, repair using a method 

approved by the Manager, ANM–116, 

Transport Airplane Directorate, FAA; or the 

EASA; or Airbus’s EASA DOA. 

(i) Within 4,500 flight cycles since first 

flight. 

(ii) Within 1,500 flight cycles after 

November 3, 2009 (the effective date of AD 

2009–20–05, Amendment 39–16028 (74 FR 

49795, September 29, 2009)). 

(h) Retained Exception to Paragraph (g) of 

This AD 

This paragraph restates the exception 

specified in paragraph (f)(4) of AD 2009–20– 

05, Amendment 39–16028 (74 FR 49795, 

September 29, 2009). Where the 

Accomplishment Instructions of Airbus 

Mandatory Service Bulletin A320–53–1195, 

Revision 02, including Appendix 01, dated 

April 5, 2007; or Airbus Mandatory Service 

Bulletin A320–53–1196, Revision 01, 

including Appendix 01, dated November 29, 

2006; as applicable; specify to submit a 

report where no damage or crack is found 

during the inspection required by paragraph 

(g)(1) or (g)(2) of this AD: Send the report to 

Airbus using the applicable reporting sheet 

in Appendix 01 of Airbus Mandatory Service 

Bulletin A320–53–1195, Revision 02, dated 

April 5, 2007; or Airbus Mandatory Service 

Bulletin A320–53–1196, Revision 01, dated 

November 29, 2006. Send the report at the 

applicable time specified in paragraph (h)(1) 

or (h)(2) of this AD. 

(1) If the inspection was done on or after 

November 3, 2009 (the effective date of AD 

2009–20–05, Amendment 39–16028 (74 FR 

49795, September 29, 2009)): Submit the 

report within 30 days after the inspection. 

(2) If the inspection was done before 

November 3, 2009 (the effective date of AD 

2009–20–05, Amendment 39–16028 (74 FR 

49795, September 29, 2009)): Submit the 

report within 30 days after November 3, 

2009. 

(i) New Repetitive Inspections and 

Corrective Action 

(1) At the latest of the times specified in 

paragraphs (i)(1)(i), (i)(1)(ii), and (i)(1)(iii) of 

this AD: Perform detailed, HFEC, and 

ultrasonic inspections (for cracking, damage, 

correct installation, and correct adjustment, 

as applicable) of the LH and RH MLG door 

actuator fitting on the keel beam, and do all 

applicable corrective actions before further 

flight. Do all actions required by this 

paragraph in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–53–1195, Revision 05, 

dated November 22, 2013; except where that 

service information specifies that the 

applicable corrective action is contacting 

Airbus, before further flight, repair using a 

method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or the EASA; or 

Airbus’s EASA DOA. Repeat the inspections 

thereafter at intervals not to exceed 2,250 

flight cycles. 

(i) Before the accumulation of 3,000 flight 

cycles since first flight. 

(ii) Within 2,250 flight cycles after the most 

recent inspection done as described in 

Airbus Service Bulletin A320–53–1195, or 

Task 533154–02–1 of the Airbus A318/A319/ 

A320/A321 Airworthiness Limitations 

Section Part 2—Damage Tolerant 

Airworthiness Limitations Items (DT ALI), as 

applicable. 

(iii) Within 1,500 flight cycles after the 

effective date of this AD. 

(2) At the latest of the times specified in 

paragraphs (i)(2)(i), (i)(2)(ii), and (i)(2)(iii) of 

this AD: Perform detailed and HFEC 

inspections (for cracking, damage, correct 

installation, and correct adjustment, as 

applicable) of the LH and RH MLG door 

hinge fitting on the keel beam, and do all 

applicable corrective actions before further 

flight. Do all actions required by this 

paragraph in accordance with the 

Accomplishment Instructions of Airbus 

Service Bulletin A320–53–1196, Revision 04, 

dated November 22, 2013; except where that 

service information specifies that the 

applicable corrective action is contacting 

Airbus, before further flight, repair using a 

method approved by the Manager, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA; or the EASA; or 

Airbus’s EASA DOA. Repeat the inspections 

thereafter at intervals not to exceed 3,000 

flight cycles. 

(i) Before the accumulation of 3,000 flight 

cycles since first flight. 

(ii) Within 3,000 flight cycles after the most 

recent inspection done as described in 

Airbus Service Bulletin A320–53–1196, or 

Task 533154–02–1 of the Airbus A318/A319/ 

A320/A321 ALS Part 2—Damage Tolerant 

Airworthiness Limitation Items (DT ALI), as 

applicable. 

(iii) Within 1,500 flight cycles after the 

effective date of this AD. 

(j) New Corrective Action Limitation 

The accomplishment of a corrective action 

on an airplane, as required by paragraph (i) 

of this AD, does not constitute terminating 

action for the repetitive inspection 

requirements of this AD for that airplane. 

(k) New Maintenance or Inspection Program 

Revision 

After the effective date of this AD and 

before further flight after doing the 

inspection required by paragraph (i) of this 

AD: Revise the maintenance or inspection 

program, as applicable, to remove Task 

533154–02–1 of the Airbus A318/A319/

A320/A321 ALS Part 2—Damage Tolerant 

Airworthiness Limitations Items (DT ALI), 

Revision 01, dated April 4, 2012; Airbus 

A318/A319/A320/A321 Airworthiness 

Limitation Items, Document AI/SE–M4/

95A.0252/96, Issue 10, dated October 2009; 

or Airbus A318/A319/A320/A321 

Airworthiness Limitation Items, Document 

AI/SE–M4/95A.0252/96 Issue 11, dated 

September 2010. The actions required by this 

AD take precedence over Task 533154–02–1 

of the Airbus A318/A319/A320/A321 ALS 

Part 2—Damage Tolerant Airworthiness 

Limitation Items (DT ALI), Revision 01, dated 

April 4, 2012; Airbus A318/A319/A320/A321 

Airworthiness Limitation Items, Document 

AI/SE–M4/95A.0252/96, Issue 10, dated 

October 2009; and Airbus A318/A319/A320/ 

A321 Airworthiness Limitation Items, 

Document AI/SE–M4/95A.0252/96 Issue 11, 

dated September 2010. 


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Federal Register / Vol. 80, No. 40 / Monday, March 2, 2015 / Rules and Regulations 11101 

(l) Credit for Previous Actions 

(1) This paragraph provides credit for 

actions required by paragraph (i)(1) of this 

AD, if those actions were performed before 

the effective date of this AD using Airbus 

Service Bulletin A320–53–1195, Revision 03, 

dated November 8, 2011; or Airbus Service 

Bulletin A320–53–1195, Revision 04, dated 

August 22, 2012; which are not incorporated 

by reference in this AD. 

(2) This paragraph provides credit for 

actions required by paragraph (i)(2) of this 

AD, if those actions were performed before 

the effective date of this AD using Airbus 

Service Bulletin A320–53–1196, Revision 02, 

dated November 8, 2011; or Airbus Service 

Bulletin A320–53–1196, Revision 03, dated 

August 22, 2012; which are not incorporated 

by reference in this AD. 

(m) Other FAA AD Provisions 

The following provisions also apply to this 

AD: 

(1) Alternative Methods of Compliance 

(AMOCs): The Manager, International 

Branch, ANM–116, Transport Airplane 

Directorate, FAA, has the authority to 

approve AMOCs for this AD, if requested 

using the procedures found in 14 CFR 39.19. 

In accordance with 14 CFR 39.19, send your 

request to your principal inspector or local 

Flight Standards District Office, as 

appropriate. If sending information directly 

to the International Branch, send it to ATTN: 

Sanjay Ralhan, Aerospace Engineer, 

International Branch, ANM–116, Transport 

Airplane Directorate, FAA, 1601 Lind 

Avenue SW., Renton, WA 98057–3356; 

telephone 425–227–1405; fax 425–227–1149. 

Information may be emailed to: 9-ANM-116- 

AMOC-REQUESTS@faa.gov. Before using 

any approved AMOC, notify your appropriate 

principal inspector, or lacking a principal 

inspector, the manager of the local flight 

standards district office/certificate holding 

district office. The AMOC approval letter 

must specifically reference this AD. 

(2) Contacting the Manufacturer: As of the 

effective date of this AD, for any requirement 

in this AD to obtain corrective actions from 

a manufacturer, the action must be 

accomplished using a method approved by 

the Manager, International Branch, ANM– 

116, Transport Airplane Directorate, FAA; or 

EASA; or Airbus’s EASA DOA. If approved 

by the DOA, the approval must include the 

DOA-authorized signature. 

(3) Reporting Requirements: A federal 

agency may not conduct or sponsor, and a 

person is not required to respond to, nor 

shall a person be subject to a penalty for 

failure to comply with a collection of 

information subject to the requirements of 

the Paperwork Reduction Act unless that 

collection of information displays a current 

valid OMB Control Number. The OMB 

Control Number for this information 

collection is 2120–0056. Public reporting for 

this collection of information is estimated to 

be approximately 5 minutes per response, 

including the time for reviewing instructions, 

completing and reviewing the collection of 

information. All responses to this collection 

of information are mandatory. Comments 

concerning the accuracy of this burden and 

suggestions for reducing the burden should 

be directed to the FAA at: 800 Independence 

Ave. SW., Washington, DC 20591, Attn: 

Information Collection Clearance Officer, 

AES–200. 

(n) Related Information 

(1) Refer to Mandatory Continuing 

Airworthiness Information (MCAI) EASA 

Airworthiness Directive 2012–0118, dated 

July 4, 2012, for related information. You 

may examine the MCAI in the AD docket on 

the Internet at http://www.regulations.gov/

#!documentDetail;D=FAA-2014-0139-0002. 

(2) Service information identified in this 

AD that is not incorporated by reference in 

this AD is available at the addresses specified 

in paragraphs (o)(5) and (o)(6) of this AD. 

(o) Material Incorporated by Reference 

(1) The Director of the Federal Register 

approved the incorporation by reference 

(IBR) of the service information listed in this 

paragraph under 5 U.S.C. 552(a) and 1 CFR 

part 51. 

(2) You must use this service information 

as applicable to do the actions required by 

this AD, unless this AD specifies otherwise. 

(3) The following service information was 

approved for IBR on April 6, 2015. 

(i) Airbus Service Bulletin A320–53–1195, 

Revision 05, dated November 22, 2013. 

(ii) Airbus Service Bulletin A320–53–1196, 

Revision 04, dated November 22, 2013. 

(4) The following service information was 

approved for IBR on November 3, 2009 (74 

FR 49795, September 29, 2009). 

(i) Airbus Mandatory Service Bulletin 

A320–53–1195, Revision 02, including 

Appendix 01, dated April 5, 2007. 

(ii) Airbus Mandatory Service Bulletin 

A320–53–1196, Revision 01, including 

Appendix 01, dated November 29, 2006. 

(5) For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EIAS, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 61 

93 44 51; email account.airworth-eas@

airbus.com; Internet http://www.airbus.com. 

(6) You may view this service information 

at the FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. For 

information on the availability of this 

material at the FAA, call 425–227–1221. 

(7) You may view this service information 

that is incorporated by reference at the 

National Archives and Records 

Administration (NARA). For information on 

the availability of this material at NARA, call 

202–741–6030, or go to: http://

www.archives.gov/federal-register/cfr/ibrlocations.html. 

Issued in Renton, Washington, on February 

4, 2015. 

Dionne Palermo, 

Acting Manager, Transport Airplane 

Directorate, Aircraft Certification Service. 

[FR Doc. 2015–02692 Filed 2–27–15; 8:45 am] 

BILLING CODE 4910–13–P 

DEPARTMENT OF TRANSPORTATION 

Federal Aviation Administration 

14 CFR Part 39 

[Docket No. FAA–2014–0189; Directorate 

Identifier 2013–NM–181–AD; Amendment 

39–18099; AD 2015–03–03] 

RIN 2120–AA64 

Airworthiness Directives; Airbus 

Airplanes 

AGENCY: Federal Aviation 

Administration (FAA), Department of 

Transportation (DOT). 

ACTION: Final rule. 

SUMMARY: We are adopting a new 

airworthiness directive (AD) for certain 

Airbus Model A300 series airplanes, 

Model A300 B4–600, B4–600R, and F4– 

600R series airplanes, and Model A300 

C4–605R Variant F airplanes 

(collectively called Model A300–600 

series airplanes). This AD was prompted 

by a report of chafing found on the 

overflow sensor harness of the surge 

tank, and subsequent contact between 

the electrical wiring and fuel tank 

structure. This AD requires a one-time 

inspection for chafing of the overflow 

sensor harness, and repair if necessary. 

This AD also requires modification of 

the sensor harness. We are issuing this 

AD to prevent chafing of the harness 

and subsequent contact between the 

electrical wiring and fuel tank structure, 

which could result in electrical arcing 

and a fuel tank explosion and 

consequent loss of the airplane. 

DATES: This AD becomes effective April 

6, 2015. 

The Director of the Federal Register 

approved the incorporation by reference 

of certain publications listed in this AD 

as of April 6, 2015. 

ADDRESSES: You may examine the AD 

docket on the Internet at http://

www.regulations.gov/

#!docketDetail;D=FAA-2014-0189 or in 

person at the Docket Management 

Facility, U.S. Department of 

Transportation, Docket Operations, M– 

30, West Building Ground Floor, Room 

W12–140, 1200 New Jersey Avenue SE., 

Washington, DC. 

For service information identified in 

this AD, contact Airbus, Airworthiness 

Office—EAW, 1 Rond Point Maurice 

Bellonte, 31707 Blagnac Cedex, France; 

telephone +33 5 61 93 36 96; fax +33 5 

61 93 44 51; email account.airwortheas@airbus.com; Internet http://

www.airbus.com. You may view this 

referenced service information at the 

FAA, Transport Airplane Directorate, 

1601 Lind Avenue SW., Renton, WA. 


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